This paper describes a new application of a low cost MEMS gyro for small satellite`s attitude determination, as well as a calibration procedure. Because of space application and there is not linear acceleration in this environment, for the first time g-dependent bias effect on sensor`s data is considered and a new method to calculate the level of this effect and elimination of that is proposed. For this aim one-axis exact rate table is used and a temperature compensation method is proposed to remove the effect of temperature variation on bias and scale factor. This measurement unit contains three orthogonally mounted MEMS gyros. Using one-axis rate table is applied to solve the problem of accessing to the three-axis one. The accuracy of sensor is considerably improved by correction of misalignment error. Experimental results verify the proposed calibration method of three axis MEMS gyro.
)